Unmanned Aircraft, Control Method, Associated Platform and High-Altitude Turbine

Abstract

Unmanned aircraft, comprising a first wing ( 11 ) and a second wing ( 12 ), wherein at least one of the first and second wings ( 11, 12 ) are made with a multiple element configuration comprising a set of wing profiles ( 21, 22, 23, 24 ) which are arranged at least partially in a condition of mutual proximity, said set of wing profiles comprising at least a first wing profile ( 21 ) and a second wing profile ( 22 ) which are mutually positioned one after the other and which define a leading edge and a trailing edge, respectively, wherein said first wing ( 11 ) and said second wing ( 12 ) are spaced with respect to each other; said aircraft further comprising interconnection supports ( 13, 14 ) between said first wing ( 11 ) and said second wing ( 12 ), holding said first and second wing ( 11, 12 ) at a given distance, said unmanned aircraft further comprising at least one aerodynamic container ( 40 ) positioned between said first wing ( 11 ) and said second wing ( 12 ), said aerodynamic container ( 40 ) comprising an inner compartment and a casing enclosing said inner compartment and being adapted and configured to carry a load and/or a central motor ( 50 c ).

1 . Unmanned aircraft, comprising a first wing ( 11 ) and a second wing ( 12 ), wherein at least one of the first and second wings ( 11 ,  12 ) are made with a multiple element configuration comprising a set of wing profiles ( 21 ,  22 ,  23 ,  24 ) which are arranged at least partially in a condition of mutual proximity, said set of wing profiles comprising at least a first wing profile ( 21 ) and a second wing profile ( 22 ) which are mutually positioned one after the other and which define a leading edge and a trailing edge, respectively, wherein said first wing ( 11 ) and said second wing ( 12 ) are spaced with respect to each other; said aircraft further comprising interconnection supports ( 13 ,  14 ) between said first wing ( 11 ) and said second wing ( 12 ), holding said first and second wing ( 11 ,  12 ) at a given distance,
 said unmanned aircraft further comprising at least one aerodynamic container ( 40 ) positioned between said first wing ( 11 ) and said second wing ( 12 ), said aerodynamic container ( 40 ) comprising an inner compartment and a casing enclosing said inner compartment and being adapted and configured to carry a load and/or a central motor ( 50   c ).   
     
     
         2 . Unmanned aircraft according to  claim 1 , comprising a plurality of motors ( 50 ), optionally a plurality of electric machines having a rotor axially fixed to a propeller ( 51 ) and/or wherein in correspondence of said first wing ( 11 ) and said second wing ( 12 ) a plurality of electric machines are present, comprising a rotor axially fixed to a propeller ( 51 ), wherein said propeller ( 51 ) is a driving propeller configured to produce, in at least a predefined condition of use, an accelerated air flow that touches and/or impinges the profile of said first wing ( 11 ) and/or said second wing ( 12 ), optionally causing, substantially at said at least one first wing ( 11 ) and/or said second wing ( 12 ), an air flow of greater speed than the speed at which said aircraft moves, and/or configured to generate a lift on said first wing ( 11 ) and/or second wing ( 12 ). 
     
     
         3 . Unmanned aircraft according to  claim 2 , comprising an operating configuration in which at least part of said plurality of motors ( 50 ) is configured to exert an action, or airbrake, optionally by means of a braking action caused by a rotation of the propellers concordant with the motion direction of the aircraft, optionally wherein, in said operating configuration, said motors ( 50 ) are controlled independently so as to each generate a variable braking force, and said aircraft is configured to perform in use a trajectory along a curve at least partially, optionally completely, followed through the variable braking action of said motors ( 50 ). 
     
     
         4 . Unmanned aircraft according to one or more of the preceding claims, comprising a retaining cable ( 18 ), wherein:
 said retaining cable ( 18 ) is a cable with low aerodynamic resistance and/or provided, for at least a portion thereof, with a lateral surface at least partially, more preferably integrally, covered with concavities or recesses adapted to favor the reduction of the aerodynamic resistance of the cable itself and/or is provided with at least a portion comprising a helical surface and/or a Savonius turbine-shaped surface; and/or wherein
 said retaining cable ( 18 ) is a cable at least partially rotating with respect to its own development axis (K), and in particular said portion having said helical surface and/or Savonius turbine-shaped surface is rotating; and/or wherein 
   said retaining cable ( 18 ) is retained, at a portion thereof, in particular end, with a rotating bearing.   
     
     
         5 . Unmanned aircraft according to  claim 4 , comprising a motor adapted to rotate at least part of said retaining cable ( 18 ), wherein—optionally—said motor comprises at least a portion fixed in correspondence of and/or on said retaining cable ( 18 ). 
     
     
         6 . Unmanned aircraft according to one or more of the preceding claims, wherein at least part of said aircraft is coated with and/or made of a material that is visible to the infrared and/or reflecting the infrared and/or visible for or reflecting wavelengths greater than 600 nm, more preferably 700 nm and/or is characterized by night visibility, and wherein in particular the retaining cable ( 18 ) has infrared visibility and/or infrared reflection properties and/or visibility or reflection of wavelengths greater than 600 nm, more preferably 700 nm and/or is characterized by night visibility. 
     
     
         7 . Unmanned aircraft according to one or more of the preceding claims, comprising a first operating, take-off and/or landing configuration, and a second operating configuration of translated flight, wherein in said first operating configuration, the propellers ( 51 ) of each of the motors ( 50 ) have an axis of rotation inclined with respect to the vertical axis, although close to being vertical and/or the longitudinal axis of said aircraft is close to being vertical, said aircraft being configured to take off against the wind and/or the first operating configuration is an operating configuration of windward take-off and/or landing, wherein the axis of rotation of the propellers is facing the direction of origin of the wind. 
     
     
         8 . Unmanned aircraft according to one or more of the preceding claims when dependent on  claim 4 , comprising a plurality of bridles, optionally 2 or 4 bridles, wherein said bridles are installed at end portions of said first wing ( 11 ) and of said second wing ( 12 ); said plurality of bridles being removably connected to said retaining cable ( 18 ). 
     
     
         9 . Aircraft according to one or more of the preceding claims, wherein the interconnection supports ( 13 ,  14 ) comprise a first and a second interconnection support ( 13 ,  14 ), and wherein said first interconnection support and/or said second interconnection support ( 13 ;  14 ) are rigid supports, optionally substantially wing shaped, and integrate movable surfaces ( 13   t ,  14   t ) comprising ailerons or rudders or flaps and/or wherein said first or second wing ( 11 ,  12 ) integrate movable surfaces, wherein said movable surfaces ( 13   t ;  14   t ) are configured to modify the flow produced by said motors ( 50 ) when activated. 
     
     
         10 . Unmanned aircraft according to one or more of the preceding claims, further comprising at least one tie rod or connecting element ( 41 ) for said aerodynamic container ( 40 ), said tie rod or connecting element ( 41 ) comprising a first portion, optionally a first end fixed to at least one between said first wing ( 11 ), said second wing ( 12 ), or an interconnection support ( 13 ,  14 ) and a second portion, distinct from said first portion and/or from said first end, optionally a second end opposite to said first end, fixed to said aerodynamic container. 
     
     
         11 . Unmanned aircraft according to  claim 10 , wherein said interconnection supports ( 13 ,  14 ) are two and comprise a first interconnection support ( 13 ) and a second interconnection support ( 14 ), said first and second interconnection support being inclined, in particular being arranged orthogonally, with respect to said first wing ( 11 ) and second wing ( 12 ) and wherein said aerodynamic container ( 40 ) is positioned between said first wing ( 11 ), said second wing ( 12 ), and said first interconnection support ( 13 ) and said second interconnection support ( 14 ) and/or wherein said aircraft ( 1 ) takes a substantially box-like shape and/or defines a shape with two parallel sides, said sides being defined by said first wing ( 11 ), said second wing ( 12 ), said first interconnection support ( 13 ) and said second interconnection support ( 14 ), said first wing ( 11 ) being offset with respect to said second wing ( 12 ) and develops substantially on a plane parallel to the plane on which the second wing ( 12 ) substantially develops;
 and wherein said first interconnection support ( 13 ) and/or said second interconnection support ( 14 ) integrate a set of wing profiles which are arranged at least partially in a condition of mutual proximity, optionally along a direction of advancement of said aircraft.   
     
     
         12 . Unmanned aircraft according to one or more of  claim 1 - 11 , wherein said first and said second interconnection support ( 13 ;  14 ) each comprise a first portion, optionally a first end, fixed at a first end of the first wing ( 11 ) and at a second end of the first wing ( 11 ), respectively, opposite to the first end, and a second portion, optionally a second end opposite to the first end, fixed at a first end of the second wing ( 12 ) and at a second end of the second wing ( 12 ), respectively, opposite to the first end, and also comprising a plurality of tie rods or connecting elements ( 41 ) each having a first end fixed at a connection point between said first interconnection support ( 13 ) or said second interconnection support ( 14 ) and the respective portion or end of the first at the wing ( 11 ) or of the second wing ( 12 ), respectively, and a second end, opposite to the first end, fixed to said aerodynamic container ( 40 ), optionally in such a way that said aerodynamic container ( 40 ) takes a substantially central and/or substantially barycentric position between said first wing ( 11 ), said second wing ( 12 ) said first interconnection support ( 13 ) and said second interconnection support ( 14 ). 
     
     
         13 . Aircraft according to one or more of the preceding claims, wherein said aerodynamic container ( 40 ) comprises a fixed central motor ( 50   c ), and wherein the central motor ( 50   c ) and/or said plurality of motors ( 50 ) comprise a plurality of electric motors whose rotor is fixed to a propeller ( 51 ), and wherein said at least one first and one second wing profile are positioned behind said propeller ( 51 ) with respect to a direction of advancement of said aircraft and/or wherein said propeller ( 51 ) is located at the front with respect to the leading edge of said first wing ( 11 ) and/or of said second wing ( 12 ). 
     
     
         14 . Aircraft according to one or more of the preceding claims, wherein said first wing ( 11 ) and/or said second wing ( 12 ) comprise a first wing portion and a second overlapping wing portion, in particular overlapping along a direction substantially orthogonal to a direction of advancement and/or comprising at least one intrados or an extrados and wherein the overlap occurs along the direction substantially identified by an ideal line joining the intrados or extrados of the first wing portion with the intrados or extrados of the second wing portion; said first wing ( 11 ) and/or said second wing ( 12 ) each comprising a plurality of dividing walls, optionally equally spaced, interposed between said first and said second wing. 
     
     
         15 . Aircraft according to one or more of the preceding claims, characterized in that it is a vertical take-off aircraft, and in that it comprises at least a first operating movement configuration substantially in vertical and/or hovering direction, in particular at take-off and/or at landing, and at least a second operating configuration of translated flight, wherein in said first operating configuration said direction of advancement is substantially vertical, and wherein in said second operating configuration the direction of advancement is substantially and/or comprises a longitudinal component. 
     
     
         16 . Aircraft according to one or more of the preceding claims, wherein said first interconnection support and/or said second interconnection support ( 13 ;  14 ) integrate movable surfaces ( 13   t ,  14   t ) comprising ailerons or rudders or flaps and/or wherein said first or second wing ( 11 ,  12 ) integrate movable surfaces, wherein said movable surfaces ( 13   t ;  14   t ) are configured to modify the flow produced by said motors ( 50 ) when activated. 
     
     
         17 . Aircraft according to  claim 2 , wherein said motors ( 50 ) are at least four, fixed, peripheral and controlled or controllable independently of each other, and at least one and more preferably each of said motors ( 50 ;  50   c ) has a variable pitch propeller ( 51 ), in particular variable between at least a first and smaller pitch and a second and greater pitch, and wherein in said first operating configuration said propeller ( 51 ) takes at least the first and smaller pitch and in said second operating configuration said propeller ( 51 ) takes the second and greater pitch. 
     
     
         18 . Control method of an unmanned aircraft ( 1 ) according to one or more of the preceding claims, said method comprising:
 an activation step of at least one motor ( 50 ) of a plurality of independently controllable motors ( 50 ) of said aircraft ( 1 ) in a first vertical take-off operating configuration or first flight attitude, starting from a support platform ( 101 ),   a step of adjusting the power generated by said plurality of motors ( 50 ) to cause a change of said first flight attitude in a further or second flight attitude identifying a second operating configuration of the aircraft ( 1 ) in which it proceeds in translated flight with a horizontal translation component,   
       wherein
 the step of adjusting the power generated by said plurality of motors ( 50 ) causes an alteration of the spatial orientation of the structure of said aircraft ( 1 ); 
 and wherein said alteration of the spatial orientation of the structure of said aircraft ( 1 ) and/or the mutation between the first and the second attitude take place by means of motors ( 50 ) rigidly joined to the structure of said aircraft ( 1 ). 
 
     
     
         19 . Method according to  claim 18 , comprising a control step of said second flight attitude wherein at least part of said motors ( 50 ) acts as an airbrake for said aircraft, optionally wherein said control step comprises an independent control of said motors ( 50 ). 
     
     
         20 . Method according to  claim 18 , wherein said control step in which at least part of said motors acts as an airbrake comprises maintaining the rotation of the propeller ( 51 ) of each propeller used as an airbrake according to the direction of advancement of the aircraft and/or comprises a braking of the propeller ( 51 ) of each propeller used as an airbrake. 
     
     
         21 . Method according to one or more of the preceding  claims 17 - 19 , comprising the control of the aircraft in said second flight attitude by means of a plurality of bridles connected at different points of the aircraft and in particular at end points of said first wing ( 11 ) and/or second wing ( 12 ), said plurality of bridles being connected to a first end of a retaining cable ( 18 ) fixed to a ground support at a predefined portion thereof, optionally at an opposite end thereof with respect to said first end. 
     
     
         22 . Plant for the production of electricity, characterized in that it comprises:
 at least one carriage ( 8 ) or a tracted device, movable along a guide ( 2 ) on a predefined path by means of the action of an aircraft ( 1 ) placed at altitude and subjected to the action of the wind;   a retaining cable ( 18 ) having a first portion configured to be connected to said aircraft ( 1 ) and a second portion connected to said carriage ( 8 );   wherein said carriage ( 8 ) comprises electric generators ( 27 ,  28 ) adapted to produce electricity from the movement of said carriage ( 8 ) along said predefined path;   wherein said aircraft ( 1 ) is an aircraft according to one or more of the preceding  claims 1 - 17 .   
     
     
         23 . Base for an unmanned aircraft ( 1 ), in particular for an aircraft according to one or more of  claims 1 - 17 , said base ( 100 ) comprising a support platform ( 101 ) for said aircraft ( 1 ) and a supporting frame adapted to space said support platform from the ground, said supporting frame comprising at least one base ( 103 ); said base being characterized in that said platform ( 101 ) is movable with respect to said base ( 103 ). 
     
     
         24 . Base according to  claim 23 , wherein said platform ( 101 ) is movable by rotation relative to said base ( 103 ) and/or configured to take a plurality of controlled inclinations with respect to said base ( 103 ). 
     
     
         25 . Base according to  claim 24 , comprising servoactuators configured to perform said rotation relative to the base ( 103 ) and/or to allow or cause the taking of a plurality of inclinations with respect to said base ( 103 ), wherein said actuators are configured to receive an actuation signal from wind meters, optionally from wind direction meters, and in particular to position said platform ( 101 ) upwind on the base of said actuation signal and/or according to at least one wind direction identified by said meters, said base further comprising a dome closure element, having at least one first open configuration and one second closed configuration, wherein in said first open configuration the closing element leaves the aircraft free to take off or land on the platform ( 101 ). 
     
     
         26 . Base according to one or more of the preceding  claims 23 - 25 , further comprising a winch or drum ( 106 ) and a retaining cable ( 18 ) at least partially wound on said drum ( 106 ) and a motor ( 105 ) acting in rotation on said drum ( 106 ) for the controlled unwinding or rewinding of said retaining cable ( 18 ), said retaining cable ( 18 ) having in use at least one portion removably connected to said aircraft ( 1 );
 said base integrating a tubular element ( 107 ), optionally a telescopic tube ( 107 ), extending obliquely with respect to said platform ( 101 ) and on which and/or within which and/or with respect to which said retaining cable ( 18 ) is made to slide or slides;   said base ( 100 ) comprising an inertial measurement unit, positioned at or substantially at said tubular element ( 107 ), optionally at a free end of said tubular element ( 107 ), said inertial measurement unit being configured and/or specifically designed and/or adapted to detect forces and/or loads, in particular bending forces and/or loads, on said tubular element ( 107 ).   
     
     
         27 . System for the production of electricity, characterized in that it comprises:
 a base ( 100 ) according to one or more of the preceding  claims 23  to  26 ,   an aircraft ( 10 ) according to one or more of the preceding  claims 1  to  11 ,   a retaining cable ( 18 ) having a first portion configured to be connected to said aircraft ( 1 );   a drum on which said retaining cable ( 18 ) is wound in a second portion thereof;   generating means for producing electricity, removably connected to said retaining cable ( 18 ) and/or to the drum on which said retaining cable ( 18 ) is connected, adapted to generate electricity from or through the unwinding and/rewinding of said retaining cable ( 18 ) on said drum by the action of a traction force, at least temporary, exerted by the aircraft ( 10 ) on said retaining cable ( 18 ),   said base ( 100 ) being installed in a fixed manner with respect to the ground and said retaining cable ( 18 ) being an electrically insulating cable.